Thermal Management System

ABSTRACT

A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.

FIELD

The present subject matter relates generally to a thermal managementsystem and a method for operating the same.

BACKGROUND

A gas turbine engine typically includes a fan and a turbomachine. Theturbomachine generally includes an inlet, one or more compressors, acombustor, and at least one turbine. The compressors compress air whichis channeled to the combustor where it is mixed with fuel. The mixtureis then ignited for generating hot combustion gases. The combustiongases are channeled to the turbine(s) which extracts energy from thecombustion gases for powering the compressor(s), as well as forproducing useful work to propel an aircraft in flight and/or to power aload, such as an electrical generator.

In at least certain embodiments, the turbomachine and fan are at leastpartially surrounded by an outer nacelle. With such embodiments, theouter nacelle defines a bypass airflow passage with the turbomachine.Additionally, the turbomachine is supported relative to the outernacelle by one or more outlet guide vanes/struts. During operation ofthe gas turbine engine, various systems may generate a relatively largeamount of heat. Thermal management systems of the gas turbine engine maycollect heat from one or more of these systems to maintain a temperatureof such systems within an acceptable operating range. The thermalmanagement systems may reject such heat through one or more heatexchangers.

However, the inventors of the present disclosure have found that furtherbenefits may be achieved by operating the thermal management system toselectively add or remove heat from various systems or locations of thegas turbine engine. Accordingly, a system and/or method for operating athermal management system in a manner to increase an efficiency of thegas turbine engine would be useful.

BRIEF DESCRIPTION

Aspects and advantages of the invention will be set forth in part in thefollowing description, or may be obvious from the description, or may belearned through practice of the invention.

In one exemplary aspect of the present disclosure, a gas turbine engineis provided. The gas turbine engine includes a compressor section, acombustion section, a turbine section, and an exhaust section arrangedin series flow; and a thermal management system operable with at leastone of the compressor section, the combustion section, the turbinesection, or the exhaust section. The thermal management system includesa first heat source assembly including a first heat source exchanger, afirst thermal fluid inlet line extending to the first heat sourceexchanger, and a first thermal fluid outlet line extending from thefirst heat source exchanger; a second heat source assembly including asecond heat source exchanger, a second thermal fluid inlet lineextending to the second heat source exchanger, and second a thermalfluid outlet line extending from the second heat source exchanger; ashared assembly including a thermal fluid line and a heat sinkexchanger, the shared assembly defining an upstream junction in fluidcommunication with the first thermal fluid outlet line and secondthermal fluid outlet line and a downstream junction in fluidcommunication with the first thermal fluid inlet line and second thermalfluid inlet line; and a controller configured to selectively fluidlyconnect the first heat source assembly or the second heat sourceassembly to the shared assembly.

In certain exemplary embodiments the first heat source exchanger is acooled cooling air heat source exchanger, and wherein the second heatsource exchanger is a waste heat recovery heat source exchanger inthermal communication with the turbine section, the exhaust section, orboth.

In certain exemplary embodiments the first heat source exchanger is awaste heat recovery heat source exchanger, or a lubrication oil heatsource exchanger.

In certain exemplary embodiments the heat sink exchanger of the sharedassembly is a fuel heat sink exchanger, a bypass passage heat sinkexchanger, a compressor discharge heat sink exchanger, a ram air heatsink exchanger, or a free stream heat sink exchanger.

In certain exemplary embodiments the thermal management system includesa valve positioned at the upstream junction of the shared assembly or atthe downstream junction of the shared assembly, and wherein thecontroller is operably coupled to the valve for selectively fluidlyconnecting the first heat source assembly or the second heat sourceassembly to the shared assembly.

In certain exemplary embodiments the shared assembly includes a thermalfluid pump for providing a flow of thermal fluid through the sharedassembly and the first heat source assembly when the controller fluidlyconnects the shared assembly to the first heat source assembly, andthrough the shared assembly and the second heat source assembly when thecontroller fluidly connects the shared assembly to the second heatsource assembly.

In certain exemplary embodiments the thermal management system isconfigured to utilize a supercritical thermal transfer fluid, andwherein the shared assembly includes a supercritical thermal fluid pumpfor providing a flow of supercritical thermal fluid through the sharedassembly and the first heat source assembly when the controller fluidlyconnects the shared assembly to the first heat source assembly, andthrough the shared assembly and the second heat source assembly when thecontroller fluidly connects the shared assembly to the second heatsource assembly.

In certain exemplary embodiments the shared assembly includes a turbinein flow communication with the thermal fluid line for extracting energyfrom a thermal fluid flow through the thermal fluid line of the sharedassembly.

In certain exemplary embodiments the gas turbine engine further includesone or more sensors for sensing data indicative of one or moreparameters of the gas turbine engine, wherein the controller of thethermal management system is operably coupled to the one or moresensors, and wherein the controller is configured to selectively fluidlyconnect the first heat source assembly or the second heat sourceassembly to the shared assembly in response to the data sensed by theone or more sensors.

In certain exemplary embodiments the first heat source assembly definesa first maximum thermal fluid throughput, wherein the second heat sourceassembly defines a second maximum thermal fluid throughput, wherein theshared assembly defines a third maximum thermal fluid throughput,wherein the first maximum thermal fluid throughput is substantiallyequal to the second maximum thermal fluid throughput, and wherein thesecond maximum thermal fluid throughput is substantially equal to thethird maximum thermal fluid throughput.

In an exemplary aspect of the present disclosure, a method is providedof operating a thermal management system for a gas turbine engine. Themethod includes providing a thermal transfer fluid through a sharedassembly of the thermal management system and to a first heat sourceassembly of the thermal management system, the shared assembly includinga heat sink exchanger; sensing data indicative of a gas turbine engineoperating parameter; and providing the thermal transfer fluid throughthe shared assembly of the thermal management system and to a secondheat source assembly of the thermal management system in response tosensing data indicative of the gas turbine engine parameter.

In certain exemplary aspects sensing data indicative of the gas turbineengine parameter includes sensing data indicative of a temperatureparameter of the gas turbine engine.

For example, in certain exemplary aspects sensing data indicative of thetemperature parameter of the gas turbine engine includes sensing dataindicative of the temperature parameter passing a predeterminedthreshold.

In certain exemplary aspects providing the thermal transfer fluidthrough the shared assembly of the thermal management system and to thefirst heat source assembly of the thermal management system includesproviding substantially all of the thermal transfer fluid from theshared assembly of the thermal management system to the first heatsource assembly of the thermal management system.

For example, in certain exemplary aspects providing the thermal transferfluid through the shared assembly of the thermal management system andto the second heat source assembly of the thermal management systemincludes providing substantially all of the thermal transfer fluid fromthe shared assembly of the thermal management system to the second heatsource assembly of the thermal management system.

In certain exemplary aspects providing the thermal transfer fluidthrough the shared assembly of the thermal management system and to thesecond heat source assembly of the thermal management system includesactuating a valve positioned at an upstream junction of the sharedassembly or at a downstream junction of the shared assembly to divertthe flow of thermal transfer fluid.

In certain exemplary aspects the method further includes increasing apressure, a flow rate, or both of the thermal transfer fluid through theshared assembly using a thermal fluid pump of the shared assembly influid communication with a thermal fluid line of the shared assembly.

In certain exemplary aspects sensing data indicative of the gas turbineengine parameter includes sensing data indicative of an operatingcondition of the gas turbine engine.

In certain exemplary aspects the first heat source assembly includes aheat source heat exchanger thermally coupled to a cooled cooling airsystem of the gas turbine engine, and wherein the second heat sourceassembly includes a waste heat recovery heat source exchanger thermallycoupled to a turbine section of the gas turbine engine, an exhaustsection of the gas turbine engine, or both.

In certain exemplary aspects providing the thermal transfer fluidthrough the shared assembly of the thermal management system and to thefirst heat source assembly of the thermal management system includespreventing a flow of thermal transfer fluid through the second heatsource assembly, and wherein providing the thermal transfer fluidthrough the shared assembly of the thermal management system and to thesecond heat source assembly of the thermal management system includespreventing a flow of thermal transfer fluid through the first heatsource assembly.

These and other features, aspects and advantages of the presentinvention will become better understood with reference to the followingdescription and appended claims. The accompanying drawings, which areincorporated in and constitute a part of this specification, illustrateembodiments of the invention and, together with the description, serveto explain the principles of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

A full and enabling disclosure of the present invention, including thebest mode thereof, directed to one of ordinary skill in the art, is setforth in the specification, which makes reference to the appendedfigures, in which:

FIG. 1 is a schematic, cross-sectional view of an exemplary gas turbineengine according to various embodiments of the present subject matter.

FIG. 2 is a simplified schematic view of a thermal management system inaccordance with an exemplary embodiment of the present disclosure.

FIG. 3 is a schematic view of a gas turbine engine in accordance withanother exemplary embodiment of the present disclosure including athermal management system in accordance with an exemplary embodiment ofthe present disclosure.

FIG. 4 is a schematic view of a gas turbine engine in accordance withyet another exemplary embodiment of the present disclosure depictingalternative exemplary aspects of a thermal management system inaccordance with various embodiments of the present disclosure.

FIG. 5 is a flow diagram of a method of operating a thermal managementsystem for a gas turbine engine in accordance with an exemplary aspectof the present disclosure.

DETAILED DESCRIPTION

Reference will now be made in detail to present embodiments of theinvention, one or more examples of which are illustrated in theaccompanying drawings. The detailed description uses numerical andletter designations to refer to features in the drawings. Like orsimilar designations in the drawings and description have been used torefer to like or similar parts of the invention.

As used herein, the terms “first”, “second”, and “third” may be usedinterchangeably to distinguish one component from another and are notintended to signify location or importance of the individual components.

The terms “forward” and “aft” refer to relative positions within a gasturbine engine or vehicle, and refer to the normal operational attitudeof the gas turbine engine or vehicle. For example, with regard to a gasturbine engine, forward refers to a position closer to an engine inletand aft refers to a position closer to an engine nozzle or exhaust.

The terms “upstream” and “downstream” refer to the relative directionwith respect to fluid flow in a fluid pathway. For example, “upstream”refers to the direction from which the fluid flows, and “downstream”refers to the direction to which the fluid flows.

The terms “coupled,” “fixed,” “attached to,” and the like refer to bothdirect coupling, fixing, or attaching, as well as indirect coupling,fixing, or attaching through one or more intermediate components orfeatures, unless otherwise specified herein.

The singular forms “a”, “an”, and “the” include plural references unlessthe context clearly dictates otherwise.

Approximating language, as used herein throughout the specification andclaims, is applied to modify any quantitative representation that couldpermissibly vary without resulting in a change in the basic function towhich it is related. Accordingly, a value modified by a term or terms,such as “about”, “approximately”, and “substantially”, are not to belimited to the precise value specified. In at least some instances, theapproximating language may correspond to the precision of an instrumentfor measuring the value, or the precision of the methods or machines forconstructing or manufacturing the components and/or systems. Forexample, the approximating language may refer to being within a 10percent margin.

Here and throughout the specification and claims, range limitations arecombined and interchanged, such ranges are identified and include allthe sub-ranges contained therein unless context or language indicatesotherwise. For example, all ranges disclosed herein are inclusive of theendpoints, and the endpoints are independently combinable with eachother.

Referring now to the drawings, wherein identical numerals indicate thesame elements throughout the figures, FIG. 1 is a schematic,cross-sectional view of a gas turbine engine in accordance with anexemplary embodiment of the present disclosure. More particularly, forthe embodiment of FIG. 1, the gas turbine engine is a high-bypassturbofan jet engine 10, referred to herein as “turbofan engine 10.” Asshown in FIG. 1, the turbofan engine 10 defines an axial direction A(extending parallel to a longitudinal centerline 12 provided forreference) and a radial direction R. In general, the turbofan engine 10includes a fan section 14 and a turbomachine 16 disposed downstream fromthe fan section 14.

The exemplary turbomachine 16 depicted generally includes asubstantially tubular outer casing 18 that defines an annular inlet 20.The outer casing 18 encases, in serial flow relationship, a compressorsection including a booster or low pressure (LP) compressor 22 and ahigh pressure (HP) compressor 24; a combustion section 26; a turbinesection including a high pressure (HP) turbine 28 and a low pressure(LP) turbine 30; and a jet exhaust nozzle section 32. The compressorsection, combustion section 26, turbine section, and exhaust nozzlesection 32 together define at least in part a core air flowpath 37through the turbomachine 16. A high pressure (HP) shaft or spool 34drivingly connects the HP turbine 28 to the HP compressor 24. A lowpressure (LP) shaft or spool 36 drivingly connects the LP turbine 30 tothe LP compressor 22.

For the embodiment depicted, the fan section 14 includes a variablepitch fan 38 having a plurality of fan blades 40 coupled to a disk 42 ina spaced apart manner. As depicted, the fan blades 40 extend outwardlyfrom disk 42 generally along the radial direction R. Each fan blade 40is rotatable relative to the disk 42 about a pitch axis P by virtue ofthe fan blades 40 being operatively coupled to a suitable actuationmember 44 configured to collectively vary the pitch of the fan blades 40in unison. The fan blades 40, disk 42, and actuation member 44 aretogether rotatable about the longitudinal axis 12 by LP shaft 36 acrossa power gear box 46. The power gear box 46 includes a plurality of gearsfor stepping down the rotational speed of the LP shaft 36 to a moreefficient rotational fan speed.

Referring still to the exemplary embodiment of FIG. 1, the disk 42 iscovered by rotatable front hub 48 aerodynamically contoured to promotean airflow through the plurality of fan blades 40. Additionally, theexemplary fan section 14 includes an annular fan casing or outer nacelle50 that circumferentially surrounds the fan 38 and/or at least a portionof the turbomachine 16. The nacelle 50 is supported relative to theturbomachine 16 by a plurality of circumferentially-spaced outlet guidevanes 52. Moreover, a downstream end 54 of the nacelle 50 extends overan outer portion of the turbomachine 16 so as to define a bypass airflowpassage 56 therebetween.

During operation of the turbofan engine 10, a volume of air 58 entersthe turbofan 10 through an associated inlet 60 of the nacelle 50 and/orfan section 14. As the volume of air 58 passes across the fan blades 40,a first portion of the air 58 as indicated by arrows 62 is directed orrouted into the bypass airflow passage 56 and a second portion of theair 58 as indicated by arrow 64 is directed or routed into the LPcompressor 22. The ratio between the first portion of air 62 and thesecond portion of air 64 is commonly known as a bypass ratio.

The pressure of the second portion of air 64 is then increased as it isrouted through the high pressure (HP) compressor 24 and into thecombustion section 26, where it is mixed with fuel and burned to providecombustion gases 66. Subsequently, the combustion gases 66 are routedthrough the HP turbine 28 and the LP turbine 30, where a portion ofthermal and/or kinetic energy from the combustion gases 66 is extracted.

The combustion gases 66 are then routed through the jet exhaust nozzlesection 32 of the turbomachine 16 to provide propulsive thrust.Simultaneously, the pressure of the first portion of air 62 issubstantially increased as the first portion of air 62 is routed throughthe bypass airflow passage 56 before it is exhausted from a fan nozzleexhaust section 76 of the turbofan 10, also providing propulsive thrust.

Further, the exemplary turbofan engine 10 includes a controller 82operably connected at least to one or more engine sensors 84. The one ormore engine sensors 84 may be configured to sense data indicative ofparameters of the turbofan engine 10 (the term “parameter” with respectto such turbofan engine 10 broadly referring to, e.g., one or more of acompressor exit pressure and/or temperature, a turbine inlettemperature, a rotational speed of the high speed components/HP shaft34, a rotational speed of the low pressure components/LP shaft 36, etc.,as well as a flight schedule parameter, such as throttle position,altitude, flight phase, etc.). The controller 82 may also be configuredto receive data, such as command data, from one or more users oroperators of the turbofan engine 10 (such as a pilot). Based on thisdata received indicative of the parameters, either by the users oroperators, or by the one or more sensors 84, the controller 82 may beconfigured to determine various gas turbine engine operating parameters,and/or an operating condition of the turbofan engine 10, such as a climboperating condition, a cruise operating condition, an idle operatingcondition, etc. The controller 82 may be configured in the same manneras the exemplary control system/ controller 108 described below withreference to FIG. 2.

Moreover, it will be appreciated that the exemplary turbofan engine 10further includes various accessory systems to aid in the operation ofthe turbofan engine 10 and/or an aircraft including the turbofan engine10. For example, the exemplary turbofan engine 10 further includes acooled cooling air (CCA) system 80 (sometimes also referred to as a“compressor cooling air system”) for cooling air from one or both of theHP compressor 24 or LP compressor 22, and providing such cooled air toone or both of the HP turbine 28 or LP turbine 30, or alternatively toan aft portion of the HP compressor 24. For example, the cooled coolingair system 80 may include a cooling duct and a heat exchanger forproviding such functionality (see, e.g., FIG. 3, below).

In addition, the exemplary turbofan engine 10 depicted in FIG. 1includes a fuel delivery system 86 for providing a fuel flow to thecombustion section 26 of the turbomachine 16 and a lubrication oilsystem 88. For the embodiment shown, the fuel delivery system 86generally includes a fuel tank 90, one or more fuel lines 92 extendingfrom the fuel tank 90 to the combustion section 26, and a fuel pump 94positioned in flow communication with the one or more fuel lines 92 forincreasing a pressure and/or flow rate of the fuel flow therethrough.Further, it will be appreciated that the lubrication oil system 88 ofthe exemplary turbofan engine 10 may be configured in a similar mannerto known systems, whereby the lubrication oil system 88 provides alubrication oil to one or more bearings of the turbofan engine 10,lubricating such bearings, and reducing a temperature of such bearings.For example, the lubrication oil system 88 may include one or morepumps, tanks, etc., labeled generally as numeral 89, to facilitate suchfunctionality.

Prior turbofan engines 10 and/or aircraft have included individual heatexchangers for each of these accessory systems to remove heat from,e.g., air and/or lubrication in such systems. However, aspects of thepresent disclosure may include a thermal management system 100 (see FIG.2) for transferring heat from such accessory systems selectively based,e.g., on an engine parameter or engine operating condition, to moreefficiently remove such heat and/or utilize such heat and moreefficiently utilize the components included (e.g., the heat sink heatexchangers). In such a manner, as will be explained further below, theturbofan engines 10 may operate these components of the thermalmanagement system 100 on an “as needed” basis and may not requireredundant components for doing so.

It should be appreciated, however, that the exemplary turbofan engine 10depicted in FIG. 1 is by way of example only, and that in otherexemplary embodiments, aspects of the present disclosure mayadditionally, or alternatively, be applied to any other suitable gasturbine engine. For example, in other exemplary embodiments, theturbofan engine 10 may include any suitable number of compressors,turbines (such as an intermediate turbine in addition to an LP and HPturbine), shafts/spools (e.g., two spools, three spools), etc. Further,in certain exemplary embodiments, aspects of the present disclosure mayfurther apply to any other suitable aeronautical gas turbine engine,such as a turbojet engine, turboshaft engine, turboprop engine, etc.,whether operated as a subsonic gas turbine engine (i.e., configured tooperate mainly at subsonic flight speeds) or as a supersonic gas turbineengine (i.e., configured to operate mainly at supersonic flight speeds).Additionally, in still other exemplary embodiments, the exemplaryturbofan engine 10 may include or be operably connected to any othersuitable accessory systems. Additionally, or alternatively, theexemplary turbofan engine 10 may not include or be operably connected toone or more of the accessory systems discussed above.

Referring now to FIG. 2, a schematic diagram is provided of a thermalmanagement system 100 in accordance with an exemplary embodiment of thepresent disclosure for incorporation at least partially into a gasturbine engine, such as the exemplary turbofan engine 10 of FIG. 1. Morespecifically, although depicted in isolation from a gas turbine enginein FIG. 2, it will be appreciated that the exemplary thermal managementsystem 100 is operable with at least one of a compressor section, acombustion section (such as combustion section 26 of FIG. 1), a turbinesection, or an exhaust section (such as exhaust section 32 of FIG. 1) ofthe gas turbine engine within which it is installed (see also, e.g.,FIG. 3).

As shown, the thermal management system 100 generally includes a firstheat source assembly 102, a second heat source assembly 104, a sharedassembly 106 and a controller 108. Each of these aspects is described ingreater detail below.

For the embodiment shown, the first heat source assembly 102 includes afirst heat source exchanger 110, a first thermal fluid inlet line 112extending to the first heat source exchanger 110, and a first thermalfluid outlet line 114 extending from the first heat source exchanger110. In such a manner, when a thermal fluid flow is directed to thefirst heat source assembly 102, such thermal fluid flow may be receivedthrough the first thermal fluid inlet line 112, provided to the firstheat source exchanger 110 from the first of thermal fluid inlet line112, and subsequently provided to the first thermal fluid outlet line114 from the first heat source exchanger 110.

Similarly for the embodiment shown, the second heat source assembly 104includes a second heat source exchanger 116, a second thermal fluidinlet line 118 extending to the second heat source exchanger 116, and asecond thermal fluid outlet line 120 extending from the second heatsource exchanger 116. In such a manner, when a thermal fluid flow isdirected to the second heat source assembly 104, such thermal fluid flowmay be received through the second thermal fluid inlet line 118,provided to the second heat source exchanger 116 from the second ofthermal fluid inlet line 118, and subsequently provided to the secondthermal fluid outlet line 120 from the second heat source exchanger 116.

As will be discussed below, e.g., with reference to FIGS. 3 and 4, thefirst heat source exchanger 110 and second heat source exchanger 116 mayeach be thermally coupled to one or more components of the gas turbineengine with which the thermal management system 100 is installed. Forexample, referring briefly back to FIG. 1, in at least certain exemplaryembodiments the first heat source exchanger 110 and/or the second heatsource exchanger 116 may be configured as a waste heat recovery heatsource exchanger (such as an exhaust waste heat recovery heat sourceexchanger in thermal communication with a turbine section, an exhaustsection 32, or both, or alternatively as an under-cowl waste heatrecovery heat source exchanger in thermal communication with an areaunderneath a cowling 18 of the turbomachine 16 and radially outward of acore air flowpath 37 of the turbomachine 16), a lubrication oil heatsource exchanger (e.g., in thermal communication with a lubrication oilsystem 88), a cooled cooling air heat source exchanger (e.g., in thermalcommunication with a cooled cooling air system 80), etc.

Referring still to FIG. 2, the shared assembly 106 of the exemplarythermal management system 100 includes a thermal fluid line 120 and aheat sink exchanger 122 thermally coupled to the thermal fluid line 120.The heat sink exchanger 122 of the shared assembly 106 of the thermalmanagement system 100 may be thermally coupled to any suitable heat sinkof the gas turbine engine. For example, referring again briefly back toFIG. 1, and as will be described in greater detail below with referenceto, e.g., FIGS. 3 and 4, in at least certain exemplary aspects the heatsink exchanger 122 of the shared assembly 106 may be configured as afuel heat sink exchanger (e.g., in thermal communication with a fueldelivery system 86), a bypass passage heat sink exchanger (e.g., inthermal communication with an airflow through a bypass passage 56), acompressor discharge heat sink exchanger (e.g., in thermal communicationwith a downstream section of a compressor section), a ram air heat sinkexchanger (e.g., in thermal communication with a ram airflow of theaircraft or gas turbine engine, such as in a military aircraft orengine), or a free stream heat sink exchanger (such as of a three streamgas turbine engine typically found in military applications), etc.

Additionally, in certain exemplary embodiments, the shared assembly 106may include a plurality of heat sink exchangers 122 arranged in series,parallel, or a combination thereof. With such a configuration, e.g.,wherein the shared assembly 106 includes a plurality of heat sinkexchangers 122, the system 100 may further be configured to bypass oneor more of the heat sink exchangers 122 based on an operating conditionof the aircraft or engine. For example, the system 100 may bypass a fanstream heat sink exchanger during high fuel flow rate conditions (e.g.,takeoff or climb conditions) such that a fuel heat sink exchangerreceives a majority of the heat, and further at relatively low fuel flowrate conditions (e.g., descent or idle conditions) may either bypass thefuel heat sink exchanger or may utilize the fuel heat sink exchanger andthe fan stream heat sink exchanger (or other secondary heat sinkexchanger).

Further, referring to FIG. 2, the exemplary thermal fluid line 120generally extends between, and defines at least in part, an upstreamjunction 124 and a downstream junction 126. The upstream junction 124,or rather, the thermal fluid line 120 of the shared assembly 106 at theupstream junction 124, is in fluid communication with the first thermalfluid outlet line 114 and the second thermal fluid outlet line 120.Further, the downstream junction 126, or rather, the thermal fluid line120 of the shared assembly 106 at the downstream junction 126, is influid communication with the first thermal fluid inlet line 112 and thesecond thermal fluid inlet line 118. In such a manner, it will beappreciated that during operation, a thermal fluid flow may be providedto the thermal fluid line 120 of the shared assembly 106 at the upstreamjunction 124 from the first thermal fluid outlet line 114, the secondthermal fluid outline, or both. Similarly, the thermal fluid flowthrough thermal fluid line 120 of the shared assembly 106 may beprovided to the first thermal fluid inlet line 112, the second thermalfluid inlet line 118, or both, at the downstream junction 126.

More specifically, for the embodiment shown, the thermal managementsystem 100 includes a valve positioned at the upstream junction 124 ofthe shared assembly 106 or at the downstream junction 126 of the sharedassembly 106. As will be explained in greater detail below, thecontroller 108 is operably coupled to the valve for selectively fluidlyconnecting the first heat source assembly 102 or the second heat sourceassembly 104 to the shared assembly 106. More specifically, still, forthe embodiment shown the thermal management system 100 includes a firstvalve 128 positioned at the upstream junction 124 and a second valve 130positioned at the downstream junction 126. In such a manner, it will beappreciated that the first valve 128 is fluidly coupled to the firstthermal fluid outlet line 114 (at a first inlet), the second thermalfluid outlet line 120 (at a second inlet), and the thermal fluid line120 of the shared assembly 106 (at an outlet); and the second valve 130is fluidly coupled to the thermal fluid line 120 of the shared assembly106 (at an inlet), the first thermal fluid inlet line 112 (at a firstoutlet), and the second thermal fluid inlet line 118 (at a secondoutlet).

Each of the first valve 128 and the second valve 130 is, for theembodiment shown, operably coupled to the controller 108, such that thecontroller 108 may actuate the first valve 128, the second valve 130, orboth, to selectively fluidly connect the first heat source assembly 102or the second heat source assembly 104 to the shared assembly 106. Insuch a manner, it will be appreciated that the first valve 128, thesecond valve 130, or both, may be variable throughput valves capable ofvarying a fluid flow, e.g., from two inputs to a single output (e.g.,the first valve 128), or from a single input between two outputs (e.g.,the second valve 130). In certain exemplary embodiments the first valve128 or the second valve 130 may be configured to vary a thermal fluidflow between two inlets (e.g., first valve 128) or two outlets (e.g.,second valve 130) at a ratio of 1:0 (i.e., 100% through a firstinlet/outlet and 0% through a second inlet/outlet) and 0:1.Additionally, or alternatively, the first valve 128 or the second valve130 may be configured to vary the ratio of thermal fluid flow to one ormore intermediate positions.

Referring back to the other operations and features of the thermalmanagement system 100 and referring still to FIG. 2, it will beappreciated that for the embodiment shown, thermal management system 100is configured to operate in a loop consisting essentially of the firstheat source assembly 102 and the shared assembly 106, or alternativelyin a loop consisting essentially of the second heat source assembly 104and the shared assembly 106. In such a manner, the thermal managementsystem 100 may not be configured to fully operate the first heat sourceassembly 102 and second heat source assembly 104 simultaneously. Morespecifically, for the embodiment shown, the first heat source assembly102 defines a first maximum thermal fluid throughput, the second heatsource assembly 104 defines a second maximum thermal fluid throughput,and the shared assembly 106 defines a third maximum thermal fluidthroughput. The first maximum thermal fluid throughput may be set by adiameter of the first thermal fluid inlet line 112, a diameter of thefirst thermal fluid outlet line 114, one or more flow characteristics ofthe first heat source exchanger 110, or a combination thereof.Similarly, the second maximum thermal fluid throughput may be set by adiameter of the second thermal fluid inlet line 118, a diameter of thesecond thermal fluid outlet line 120, one or more flow characteristicsof the second heat source exchanger 110, or a combination thereof.Further, the third maximum thermal fluid throughput may be set by adiameter of the thermal fluid line 120, one or more flow characteristicsof the heat sink exchanger 122, or a combination thereof.

For the embodiment depicted, the first maximum thermal fluid throughputis substantially equal to the second maximum thermal fluid throughput,and the second maximum thermal fluid throughput is substantially equalto the third maximum thermal fluid throughput. In such a manner, theshared assembly 106 of the thermal management system 100 may beconfigured to operate fully with the first heat source assembly 102, oralternatively fully with the second heat source assembly 104, but notfully with the first heat source assembly 102 and the second heat sourceassembly 104.

Moreover, it will further be appreciated that for the embodimentdepicted in FIG. 2, the shared assembly 106 further includes a thermalfluid pump 132 and a turbine 134. The thermal fluid pump 132 isconfigured to provide a flow of thermal fluid through the first heatsource assembly 102 and the shared assembly 106 when the shared assembly106 is fluidly coupled to the first heat source assembly 102 (by thecontroller 108, as will be explained below). Similarly, the thermalfluid pump 132 is configured to provide a flow of thermal fluid throughthe second heat source assembly 104 and the shared assembly 106 when theshared assembly 106 is fluidly coupled to the second heat sourceassembly 104 (again by the controller 108, as will be explained below).

More specifically, still, for the embodiment shown the thermalmanagement system 100 is configured to utilize a supercritical thermaltransfer fluid, and the thermal fluid pump 132 of the shared assembly106 is a supercritical thermal fluid pump. For example, the thermalmanagement system 100 may utilize a supercritical CO2, or othersupercritical thermal fluid. Utilization of a supercritical thermalfluid my allow for more efficient heat transfer with the thermalmanagement system 100. Further, since the thermal management system 100utilizes shared assets (i.e., the shared assembly 106) between the firstand second heat source assemblies 102, 104, the thermal managementsystem 100 may more fully utilize the more efficient heat transferfeatures throughout an entire flight envelope.

Alternatively, however, in other embodiments, the thermal managementsystem 100 utilize any other suitable thermal transfer fluid. Forexample, in other embodiments, the thermal management system 100 mayutilize a single phase thermal transfer fluid (configured to remainsubstantially in e.g., a liquid phase throughout operations), a phasechange thermal transfer fluid, etc. For example, the thermal transferfluid may be an oil, refrigerant, etc.

Further, as noted above, the exemplary shared assembly 106 includes aturbine 134. The turbine 134 may be configured to extract energy fromthe thermal transfer fluid flow through the shared assembly 106, andmore specifically, through the thermal fluid line 120 of the sharedassembly 106. In certain exemplary embodiments, the turbine 134 mayexpand the thermal transfer fluid through such extraction of energy/rotational energy therefrom, and transfer such energy to, e.g., anelectric machine to generate electrical power. Additionally, oralternatively, the turbine 134 may in other embodiments be mechanicallycoupled to the thermal fluid pump 132, such that the pump 132 isconfigured as a turbopump.

Notably, it will be appreciated that for the embodiment shown, thethermal fluid pump 132 is positioned upstream of the heat sink exchanger122, and the heat sink exchanger 122 is positioned upstream of theturbine 134, all within the shared assembly 106, and more particularly,along the thermal fluid line 120 of the shared assembly 106. In such amanner, it will be appreciated that the thermal fluid pump 132 mayincrease a pressure, a flowrate, and/or a temperature of the thermaltransfer fluid, allowing for increased thermal transfer from the thermalfluid through the heat sink exchanger 122 to a particular heat sink.Further, the turbine 134 being positioned downstream of the heat sinkexchanger 122 may further reduce the temperature of the thermal transferfluid through the shared assembly 106, prior to such thermal transferfluid being utilized to accept heat from the first heat source assembly102, the second heat source assembly 104, or both. Such may furtherincrease an efficiency of the thermal management system 100.

It should be appreciated, however, that in other exemplary embodiments,the thermal management system 100 may be configured in any othersuitable manner. For example, in other embodiments, the pump 132, heatsink exchanger 122, and turbine 134 may be arranged in any othersuitable flow order. Further, in other embodiments the shared assembly106 may not include each of the features depicted, such as the turbine134, one of the valves 128, 130, etc.

Referring still to FIG. 2, as briefly noted above, the gas turbineengine, the thermal management system 100, or both, further includes aplurality of sensors operably coupled to the controller 108. The one ormore sensors may include one or more gas turbine engine sensors 84configured to sense data indicative of, e.g., operating conditionsand/or operating parameters of the gas turbine engine, as well as one ormore thermal management system sensors. Specifically, for the embodimentshown, the thermal management system 100 includes a first sensor 136operable with the first heat source assembly 102, a second sensor 138operable with the second heat source assembly 104, and a third sensor140 and a fourth sensor 142 operable with the shared assembly 106. Thefirst sensor 136 may sense data indicative of a flow rate, a pressure,and/or a temperature of a thermal fluid flow through the first heatsource assembly 102; the second sensor 138 may similarly sense dataindicative of a flow rate, a pressure, and/or a temperature of a thermalfluid flow through the second heat source assembly 104; and the thirdsensor 140 and fourth sensor 142 may sense data indicative of a flowrate, a pressure, and/or a temperature of a thermal fluid flow throughthe shared assembly 106.

As noted, the exemplary controller 108 depicted in FIG. 2 is configuredto receive the data sensed from the one or more sensors (sensors 84,136, 138, 140, 142 for the embodiment shown) and, e.g., may make controldecisions for the thermal management system 100 based on the receiveddata.

In one or more exemplary embodiments, the controller 108 depicted inFIG. 2 may be a stand-alone controller 108 for the thermal managementsystem 100, or alternatively, may be integrated into one or more of acontroller for the gas turbine engine with which the thermal managementsystem 100 is integrated, a controller for an aircraft including the gasturbine engine with which the thermal management system 100 isintegrated, etc.

Referring particularly to the operation of the controller 108, in atleast certain embodiments, the controller 108 can include one or morecomputing device(s) 144. The computing device(s) 144 can include one ormore processor(s) 144A and one or more memory device(s) 144B. The one ormore processor(s) 144A can include any suitable processing device, suchas a microprocessor, microcontroller, integrated circuit, logic device,and/or other suitable processing device. The one or more memorydevice(s) 144B can include one or more computer-readable media,including, but not limited to, non-transitory computer-readable media,RAM, ROM, hard drives, flash drives, and/or other memory devices.

The one or more memory device(s) 144B can store information accessibleby the one or more processor(s) 144A, including computer-readableinstructions 144C that can be executed by the one or more processor(s)144A. The instructions 144C can be any set of instructions that whenexecuted by the one or more processor(s) 144A, cause the one or moreprocessor(s) 144A to perform operations. In some embodiments, theinstructions 144C can be executed by the one or more processor(s) 144Ato cause the one or more processor(s) 144A to perform operations, suchas any of the operations and functions for which the controller 108and/or the computing device(s) 144 are configured, the operations foroperating a thermal management system 100 (e.g, method 200), asdescribed herein, and/or any other operations or functions of the one ormore computing device(s) 144. The instructions 144C can be softwarewritten in any suitable programming language or can be implemented inhardware. Additionally, and/or alternatively, the instructions 144C canbe executed in logically and/or virtually separate threads onprocessor(s) 144A. The memory device(s) 144B can further store data 144Dthat can be accessed by the processor(s) 144A. For example, the data144D can include data indicative of power flows, data indicative ofengine/ aircraft operating conditions, and/or any other data and/orinformation described herein.

The computing device(s) 144 can also include a network interface 144Eused to communicate, for example, with the other components of thethermal management system 100, the gas turbine engine incorporatingthermal management system 100, the aircraft incorporating the gasturbine engine, etc. For example, in the embodiment depicted, as notedabove, the gas turbine engine and/or thermal management system 100includes one or more sensors for sensing data indicative of one or moreparameters of the gas turbine engine, the thermal management system 100,or both. The controller 108 the thermal management system 100 isoperably coupled to the one or more sensors through, e.g., the networkinterface, such that the controller 108 may receive data indicative ofvarious operating parameters sensed by the one or more sensors duringoperation. Further, for the embodiment shown the controller 108 isoperably coupled to, e.g., the first valve 128 and the second valve 130.In such a manner, the controller 108 may be configured to selectivelyfluidly connect the first heat source assembly 102 or the second heatsource assembly 104 to the shared assembly 106 (i.e., through actuationof the first valve 128, the second valve 130, or both) in response to,e.g., the data sensed by the one or more sensors.

The network interface 144E can include any suitable components forinterfacing with one or more network(s), including for example,transmitters, receivers, ports, controllers, antennas, and/or othersuitable components.

The technology discussed herein makes reference to computer-basedsystems and actions taken by and information sent to and fromcomputer-based systems. One of ordinary skill in the art will recognizethat the inherent flexibility of computer-based systems allows for agreat variety of possible configurations, combinations, and divisions oftasks and functionality between and among components. For instance,processes discussed herein can be implemented using a single computingdevice or multiple computing devices working in combination. Databases,memory, instructions, and applications can be implemented on a singlesystem or distributed across multiple systems. Distributed componentscan operate sequentially or in parallel.

Referring now to FIG. 3, a simplified, schematic view of a gas turbineengine 10 including a thermal management system 100 in accordance withan exemplary aspect of the present disclosure is depicted. The exemplarythermal management system 100 of FIG. 3 may be configured insubstantially the same manner as the exemplary thermal management system100 of FIG. 2, and the exemplary gas turbine 10 depicted in FIG. 3 maybe configured in substantially the same manner as the exemplary turbofanengine 10 described above with reference to FIG. 1, or in accordancewith any other suitable gas turbine engine (e.g., a turbofan enginehaving any other suitable configuration, a turboshaft engine, aturboprop engine, a turbojet engine, etc.).

The exemplary gas turbine engine 10 of FIG. 3 generally includes a fansection 14 and a turbomachine 16. The turbomachine 16 includes in serialflow order a compressor section having an LP compressor 22 and an HPcompressor 24, a combustion section 26, a turbine section including anHP turbine 28 and an LP turbine 30, and an exhaust section 32. Moreover,the turbomachine 16 and fan section 14 are at least partially surroundedby an outer nacelle 50, with the turbomachine 16 supported relative tothe outer nacelle 50 through a plurality of outlet guide vanes 52. Theouter nacelle 50 defines a bypass airflow passage 56 with theturbomachine 16. A first portion 62 of an airflow from the fan section14 is provided through the turbomachine 16 as a core airflow, and asecond 64 portion of the airflow from the fan section 14 is providedthrough the bypass airflow passage 56 as a bypass airflow.

In addition, the gas turbine engine 10 includes a cooled cooling airsystem 80 (sometimes also referred to as a “compressor cooling airsystem”) for providing air from one or both of the HP compressor 24 orLP compressor 22, cooling such air, and providing such air to one orboth of the HP turbine 28 or LP turbine 30 during operation of the gasturbine engine 10 (or alternatively to an aft portion of the HPcompressor 24). The cooling air system 80 includes one or more coolingpassages 81 for ducting air from the compressor section to the turbinesection, such that the cooling air system 80 may cool one or morecomponents of the turbine section.

Further, the thermal management system 100 generally includes a firstheat source assembly 102, a second heat source assembly 104, a sharedassembly 106, and a controller 108. As discussed in greater detail abovewith reference to FIG. 2, the first heat source assembly 102 generallyincludes a first heat source exchanger 110, a first thermal fluid inletline 112 (not labeled for clarity), and a first thermal fluid outletline 114 (not labeled for clarity). Additionally, the second heat sourceassembly 104 similarly includes a second heat source exchanger 116, asecond thermal fluid inlet line 118 (not labeled for clarity), and asecond thermal fluid outlet line (not labeled for clarity). Further, theshared assembly 106 generally includes a thermal fluid line 120 and aheat sink exchanger 122 thermally coupled to the thermal fluid line 120.

For the embodiment shown, the first heat source exchanger 110 of thefirst heat source assembly 102 is at least one of a cooled cooling airheat source exchanger (i.e., thermally coupled to, e.g., the one or morecooling passages 81 of the cooling air system 80 for cooling an airflowthrough the one or more cooling passages 81), an exhaust waste heatrecovery heat source exchanger (e.g., positioned at an aft end of theturbine section of the gas turbine engine 10, within the exhaust section32 of the gas turbine engine 10, or both, for extracting heat from anairflow therethrough), a lubrication oil heat source exchanger (e.g.,positioned in thermal communication with the lubrication oil system ofthe gas turbine engine 10 for extracting heat from a flow of lubricationoil therethrough), or an under-cowl waste heat recovery heat sourceexchanger (e.g., positioned within a cowling 18 of a turbomachine 16 ofthe gas turbine engine 10 for extracting heat therefrom). Morespecifically, for the embodiment of FIG. 3, the first heat sourceexchanger 110 is a cooled cooling air heat source exchanger in thermalcommunication with the cooled cooling air system 80 and the second heatsource exchanger 116 is a waste heat recovery heat source exchanger (orrather, an exhaust waste heat recovery heat source exchanger) in thermalcommunication with the turbine section, the exhaust section 32, or both.

Further, for the embodiment shown the heat sink exchanger 122 of theshared assembly 106 is at least one of a fuel heat sink exchanger (e.g.,a heat exchanger thermally coupled to the fuel delivery system fortransferring heat to a fuel flow through the fuel delivery system), abypass passage heat sink exchanger (e.g., a heat exchanger positionedwithin, or thermally coupled to, the bypass passage 56 of the gasturbine engine 10 for transferring heat to a bypass airflow through thebypass passage 56), or a compressor discharge heat sink exchanger (i.e.,a heat exchanger positioned at a downstream end of the compressorsection and upstream of the combustion section 26 for transferring heatto the airflow through, or from, the downstream end of the compressorsection of the gas turbine engine 10). More specifically, for theembodiment shown, the heat sink exchanger 122 is a fuel heat sinkexchanger.

Moreover, as discussed above, the controller 108 is configured toselectively fluidly connect the first heat source assembly 102 or thesecond heat source assembly 104 to the shared assembly 106. In such amanner, the controller 108 may operate the thermal management system 100such that the thermal management system 100 more efficiently utilizesits assets throughout a flight envelope. For example, during a firstoperating condition (e.g., cruise, decent, or some other mid- tolow-power operating mode), the controller 108 of the thermal managementsystem 100 may fluidly connect the first heat source assembly 102 withthe shared assembly 106, such that substantially all of a flow ofthermal transfer fluid through the shared assembly 106 is provided toand circulated through the first heat source assembly 102. In such amanner, the thermal management system 100 may effectively recapturewaste heat through the exhaust section 32 of the gas turbine engine 10and utilize that heat to create a more efficient combustion process byheating a fuel flow to the combustion section 26. Subsequently, during asecond operating condition (e.g., takeoff, climb, or some otherhigh-power operating mode), the controller 108 of the thermal managementsystem 100 may fluidly connect the second heat source assembly 104 withthe shared assembly 106, such that substantially all of a flow ofthermal transfer fluid through the shared assembly 106 is provided toand circulated through the second heat source assembly 104. In such amanner, the thermal management system 100 may effectively reduce atemperature of an airflow through the cooled cooling air system 80 ofthe gas turbine engine, to allow increased temperatures within theturbine section and consequently, higher power outlets of the gasturbine engine.

Notably, during the first operating mode, the cooled cooling air system80 may not need the additional heat rejection to allow the additionalpower output of the engine 10. Similarly, during the second operatingmode, it may not be necessary (or it may at least be less important) tocapture waste heat from the exhaust section 32 for short-term efficiencybenefits. Accordingly, by utilizing the shared assembly 104, which maybe selectively fluidly connected to the first heat source assembly 102and second heat source assembly 104, the thermal management system 100may operate with less non-utilized components throughout the entireflight envelope of the engine 10, providing a lighter, more efficient,and more cost effective engine.

It will be appreciated, however, that in other embodiments, the gasturbine engine 10, the thermal management system 100, or both may haveany other suitable configuration. For example, referring now to FIG. 4,it will be appreciated that in other embodiments, the first heat sourceexchanger 110 of the first heat source assembly 102 may be any othersuitable heat source exchanger, the second heat source exchanger 116 ofthe second heat source assembly 104 may be any other suitable sourceexchanger, and further the heat sink exchanger 122 of the sharedassembly 106 may be any other suitable heat sink exchanger. For example,for the embodiment depicted in FIG. 4, the first heat source exchanger110 and/or the second heat source exchanger 116 may be configured as anexhaust waste heat recovery heat exchanger 110A/ 116A, a lubrication oilheat source exchanger 110B/ 116B (operable with a lubrication oil systemof the gas turbine engine 10), an under-cowl waste heat recovery heatsource exchanger 110C/ 116C, etc. Similarly, for the embodiment of FIG.4, the heat sink exchanger 122 may be, e.g., a fuel heat sink exchanger122A (operable with a fuel delivery system 86 of the gas turbine engine10), a bypass passage heat sink exchanger 122B (e.g., coupled to, orintegrated into, an outlet guide vane 52), a compressor discharge heatsink exchanger 122C, etc. Other configurations are contemplated as well.Moreover, in still other embodiments, the heat source exchanger 110 maybe an intercooler heat source exchanger positioned within or upstream ofthe compressor section, such as upstream of the HP compressor 24, orupstream of the LP compressor 22.

Referring now to FIG. 5, a flow diagram of a method 200 for operating athermal management system of a gas turbine engine is provided. In atleast certain exemplary aspects, the method 200 may be utilized tooperate one or more of the exemplary thermal management systems 100described above with reference to FIGS. 1 through 4. However, in otherexemplary aspects, the method 200 may be utilized to operate any othersuitable thermal management system.

The method 200 generally includes at (202) providing a thermal transferfluid through a shared assembly of the thermal management system and toa first heat source assembly of the thermal management system. Theshared assembly includes a heat sink exchanger. Notably, for theexemplary aspect depicted in FIG. 5, providing the thermal transferfluid through the shared assembly of the thermal management system andto the first heat source assembly of the thermal management system at(202) includes at (204) providing substantially all of the thermaltransfer fluid from the shared assembly of the thermal management systemto the first heat source assembly of the thermal management system. Morespecifically, for the exemplary aspect depicted in FIG. 5, providing thethermal transfer fluid through the shared assembly of the thermalmanagement system and to the first heat source assembly of the thermalmanagement system at (202) includes at (206) preventing a flow ofthermal transfer fluid through a second heat source assembly.

The method 200 further includes at (208) sensing data indicative of agas turbine engine operating parameter. In certain exemplary aspects,sensing data indicative of the gas turbine engine operating parameter at(208) includes at (210) sensing data indicative of an operatingcondition of the gas turbine engine. The operating condition of the gasturbine engine may be, e.g., an operating mode of the gas turbine engineor aircraft including the gas turbine engine, such as a takeoffoperating mode, a climb operating mode, a cruise operating mode, a stepclimb operating mode, a descent operating mode, a taxiing operatingmode, a throttle position, etc. Additionally, or alternatively, incertain exemplary aspects, such as the exemplary aspect depicted in FIG.5, sensing data indicative of the gas turbine engine operating parameterat (208) includes at (212) sensing data indicative of a temperatureparameter of the gas turbine engine. More specifically, for theexemplary aspect depicted, sensing data indicative of the temperatureparameter the gas turbine engine at (212) includes at (214) sensing dataindicative of the temperature parameter passing the predeterminedthreshold. For example, sensing data indicative of the temperatureparameter passing a predetermined threshold may include sensing dataindicative of the temperature parameter surpassing a predeterminedthreshold or falling below a predetermined threshold. By way of exampleonly, in certain exemplary aspects, sensing data indicative of thetemperature parameter passing a predetermined threshold may includesensing data indicative of, e.g., a compressor exit temperatureincreasing above a predetermined threshold, an exhaust temperatureincreasing above a predetermined threshold, one or both of thecompressor exit temperature or exhaust temperature decreasing below apredetermined threshold, etc.

Notably, in one or more of the above exemplary aspects, sensing dataindicative of a gas turbine engine operating parameter at (208) mayinclude receiving data from one or more sensors within the gas turbineengine or otherwise operable with the gas turbine engine.

Referring still to the exemplary method 200 depicted in FIG. 5, themethod 200 further includes at (216) providing the thermal transferfluid through the shared assembly of the thermal management system andto the second heat source assembly of the thermal management system inresponse to sensing data indicative of the gas turbine engine operatingparameter at (208). For the exemplary aspect depicted, providing thethermal transfer fluid through the shared assembly of the thermalmanagement system and to the second heat source assembly of thermalmanagement system at (216) includes at (218) providing substantially allof the thermal transfer fluid from the shared assembly of the thermalmanagement system to the second heat source assembly of the thermalmanagement system. More specifically, for the exemplary aspect depicted,providing the thermal transfer fluid through the shared assembly of thethermal management system and to the second heat source assembly of thethermal management system at (216) includes at (220) preventing the flowof thermal transfer fluid through the first heat source assembly.

Further, for the exemplary aspect depicted in FIG. 5, providing thethermal transfer fluid through the shared assembly of the thermalmanagement system and to the second heat source assembly of the thermalmanagement system at (216) includes at (222) actuating a valvepositioned at an upstream junction of the shared assembly or at adownstream junction of the shared assembly to divert the flow of thermaltransfer fluid. In such a manner, the valve may be actuated in responseto the sensed data indicative of the gas turbine engine parameter tofluidly connect the shared assembly with the second heat source assemblyas opposed to the first heat source assembly.

Notably, in at least certain exemplary aspects, the first heat sourceassembly may include a heat source heat exchanger thermally coupled to acooled cooling air system of the gas turbine engine, and the second heatsource assembly may include a waste heat recovery heat source exchangerthermally coupled to a turbine section gas turbine engine, an exhaustsection of the gas turbine engine, or both. In such a manner, the method200 may operate the thermal management system such that the sharedassembly operates with the first heat source assembly (including theheat source heat exchanger thermally coupled to the cooled cooling airsystem) during, e.g., a high power operating mode/ conditions of the gasturbine engine such that the gas turbine engine may provide cooler airto the turbine section allowing for higher temperature combustion andgreater power generation. By contrast, the method 200 may operate thethermal management system such that the shared assembly operates withthe second heat source assembly (including the waste heat recovery heatsource exchanger) during, e.g., a cruise operating mode/condition orother relatively low-power operation modes/conditions of the gas turbineengine such that waste heat may be recovered and utilized to increase anefficiency of the gas turbine engine when the high-powered operations(requiring full use of the cooled cooling air systems) are notnecessary.

Briefly, referring still to the exemplary method 200 depicted in FIG. 5,the method 200 may additionally include at (224) increasing a pressure,a flow rate, or both of the thermal transfer fluid through the sharedassembly using a thermal fluid pump of the shared assembly in fluidcommunication with a thermal fluid line of the shared assembly.

This written description uses examples to disclose the invention,including the best mode, and also to enable any person skilled in theart to practice the invention, including making and using any devices orsystems and performing any incorporated methods. The patentable scope ofthe invention is defined by the claims, and may include other examplesthat occur to those skilled in the art. Such other examples are intendedto be within the scope of the claims if they include structural elementsthat do not differ from the literal language of the claims, or if theyinclude equivalent structural elements with insubstantial differencesfrom the literal languages of the claims.

What is claimed is:
 1. A gas turbine engine comprising: a compressor section, a combustion section, a turbine section, and an exhaust section arranged in series flow; and a thermal management system operable with at least one of the compressor section, the combustion section, the turbine section, or the exhaust section, the thermal management system comprising a first heat source assembly comprising a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly comprising a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly comprising a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.
 2. The gas turbine engine of claim 1, wherein the first heat source exchanger is a cooled cooling air heat source exchanger, and wherein the second heat source exchanger is a waste heat recovery heat source exchanger in thermal communication with the turbine section, the exhaust section, or both.
 3. The gas turbine engine of claim 1, wherein the first heat source exchanger is a waste heat recovery heat source exchanger, or a lubrication oil heat source exchanger.
 4. The gas turbine engine of claim 1, wherein the heat sink exchanger of the shared assembly is a fuel heat sink exchanger, a bypass passage heat sink exchanger, a compressor discharge heat sink exchanger, a ram air heat sink exchanger, or a free stream heat sink exchanger.
 5. The gas turbine engine of claim 1, wherein the thermal management system includes a valve positioned at the upstream junction of the shared assembly or at the downstream junction of the shared assembly, and wherein the controller is operably coupled to the valve for selectively fluidly connecting the first heat source assembly or the second heat source assembly to the shared assembly.
 6. The gas turbine engine of claim 1, wherein the shared assembly comprises a thermal fluid pump for providing a flow of thermal fluid through the shared assembly and the first heat source assembly when the controller fluidly connects the shared assembly to the first heat source assembly, and through the shared assembly and the second heat source assembly when the controller fluidly connects the shared assembly to the second heat source assembly.
 7. The gas turbine engine of claim 1, wherein the thermal management system is configured to utilize a supercritical thermal transfer fluid, and wherein the shared assembly comprises a supercritical thermal fluid pump for providing a flow of supercritical thermal fluid through the shared assembly and the first heat source assembly when the controller fluidly connects the shared assembly to the first heat source assembly, and through the shared assembly and the second heat source assembly when the controller fluidly connects the shared assembly to the second heat source assembly.
 8. The gas turbine engine of claim 1, wherein the shared assembly comprises a turbine in flow communication with the thermal fluid line for extracting energy from a thermal fluid flow through the thermal fluid line of the shared assembly.
 9. The gas turbine engine of claim 1, further comprising: one or more sensors for sensing data indicative of one or more parameters of the gas turbine engine, wherein the controller of the thermal management system is operably coupled to the one or more sensors, and wherein the controller is configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly in response to the data sensed by the one or more sensors.
 10. The gas turbine engine of claim 1, wherein the first heat source assembly defines a first maximum thermal fluid throughput, wherein the second heat source assembly defines a second maximum thermal fluid throughput, wherein the shared assembly defines a third maximum thermal fluid throughput, wherein the first maximum thermal fluid throughput is substantially equal to the second maximum thermal fluid throughput, and wherein the second maximum thermal fluid throughput is substantially equal to the third maximum thermal fluid throughput.
 11. A method of operating a thermal management system for a gas turbine engine, the method comprising: providing a thermal transfer fluid through a shared assembly of the thermal management system and to a first heat source assembly of the thermal management system, the shared assembly comprising a heat sink exchanger; sensing data indicative of a gas turbine engine operating parameter; and providing the thermal transfer fluid through the shared assembly of the thermal management system and to a second heat source assembly of the thermal management system in response to sensing data indicative of the gas turbine engine parameter.
 12. The method of claim 11, wherein sensing data indicative of the gas turbine engine parameter comprises sensing data indicative of a temperature parameter of the gas turbine engine.
 13. The method of claim 12, wherein sensing data indicative of the temperature parameter of the gas turbine engine comprises sensing data indicative of the temperature parameter passing a predetermined threshold.
 14. The method of claim 11, wherein providing the thermal transfer fluid through the shared assembly of the thermal management system and to the first heat source assembly of the thermal management system comprises providing substantially all of the thermal transfer fluid from the shared assembly of the thermal management system to the first heat source assembly of the thermal management system.
 15. The method of claim 14, wherein providing the thermal transfer fluid through the shared assembly of the thermal management system and to the second heat source assembly of the thermal management system comprises providing substantially all of the thermal transfer fluid from the shared assembly of the thermal management system to the second heat source assembly of the thermal management system.
 16. The method of claim 11, wherein providing the thermal transfer fluid through the shared assembly of the thermal management system and to the second heat source assembly of the thermal management system comprises actuating a valve positioned at an upstream junction of the shared assembly or at a downstream junction of the shared assembly to divert the flow of thermal transfer fluid.
 17. The method of claim 11, further comprising: increasing a pressure, a flow rate, or both of the thermal transfer fluid through the shared assembly using a thermal fluid pump of the shared assembly in fluid communication with a thermal fluid line of the shared assembly.
 18. The method of claim 11, wherein sensing data indicative of the gas turbine engine parameter comprises sensing data indicative of an operating condition of the gas turbine engine.
 19. The method of claim 11, wherein the first heat source assembly includes a heat source heat exchanger thermally coupled to a cooled cooling air system of the gas turbine engine, and wherein the second heat source assembly includes a waste heat recovery heat source exchanger thermally coupled to a turbine section of the gas turbine engine, an exhaust section of the gas turbine engine, or both.
 20. The method of claim 11, wherein providing the thermal transfer fluid through the shared assembly of the thermal management system and to the first heat source assembly of the thermal management system comprises preventing a flow of thermal transfer fluid through the second heat source assembly, and wherein providing the thermal transfer fluid through the shared assembly of the thermal management system and to the second heat source assembly of the thermal management system comprises preventing a flow of thermal transfer fluid through the first heat source assembly. 